Static guide vane with internal hollow channels

Abstract

A static guide vane for use in a fan section of a gas turbine engine includes an outer platform and an inner platform. The inner and outer platforms are connected by an airfoil. The airfoil have channels extending into a main body of the airfoil to reduce the weight of the vane. A cover closes off the channels with the cover providing a portion of the airfoil.

1 . A static guide vane for a gas turbine engine comprising:
 an outer platform and an inner platform, said inner and outer platforms connected by an airfoil; and   said airfoil having channels extending into a main body of said airfoil and a cover closing off said channels with said cover providing a portion of said airfoil.   
     
     
         2 . The static guide vane as set forth in  claim 1 , wherein there are a plurality of said channels extending in a generally radial direction from said inner platform toward said outer platform, and spaced from a leading edge of said airfoil towards a trailing edge of said airfoil. 
     
     
         3 . The static guide vane as set forth in  claim 2 , wherein said channels extend for a greater width, with the width defined between the leading and trailing edges, as the channels approach the trailing edge. 
     
     
         4 . The static guide vane as set forth in  claim 2 , wherein there are ribs intermediate said plurality of channels. 
     
     
         5 . The static guide vane as set forth in  claim 4 , wherein said ribs, and portions of a recess between said channels and said trailing and leading edges together form a planar surface for supporting said cover. 
     
     
         6 . The static guide vane as set forth in  claim 1 , wherein there are a plurality of said channels extending in a generally radial direction from said inner platform toward said outer platform, and spaced from a leading edge of said airfoil towards a trailing edge of said airfoil, said channels extend for a greater width, with the width defined between the leading and trailing edges, as the channels approach the trailing edge, there are ribs intermediate said plurality of channels, and portions of a recess between said channels and said trailing and leading edges together form a planar surface for supporting said cover. 
     
     
         7 . The static guide vane as set forth in  claim 1 , wherein a feature ensures that said cover is an appropriate cover for the particular static guide vane. 
     
     
         8 . A fan section for use in a gas turbine engine comprising:
 a fan rotor; and   a static guide vane, the static guide vane having an outer platform and an inner platform, said inner and outer platforms connected by an airfoil, said airfoil having channels extending into a main body of said airfoil, and a cover closing off said channels with said cover providing a portion of said airfoil.   
     
     
         9 . The fan section as set forth in  claim 8 , wherein there are a plurality of said channels extending in a generally radial direction from said inner platform toward said outer platform, and spaced from a leading edge of said airfoil towards a trailing edge of said airfoil. 
     
     
         10 . The fan section as set forth in  claim 9 , wherein said channels extend for a greater width, with the width defined between the leading and trailing edges as the channels approach the trailing edge. 
     
     
         11 . The fan section as set forth in  claim 9 , wherein there are ribs intermediate said plurality of channels. 
     
     
         12 . The fan section as set forth in  claim 11 , wherein said ribs, and portions of a recess between said channels and said trailing and leading edges together form a planar surface for supporting said cover. 
     
     
         13 . The fan section as set forth in  claim 8 , wherein there are a plurality of said channels extending in a generally radial direction from said inner platform toward said outer platform, and spaced from a leading edge of said airfoil towards a trailing edge of said airfoil, said channels extend for a greater width, with the width defined between the leading and trailing edges, as the channels approach the trailing edge, there are ribs intermediate said plurality of channels, and portions of a recess between said channels and said trailing and leading edges together form a planar surface for supporting said cover. 
     
     
         14 . The fan section as set forth in  claim 8 , wherein a feature ensures that said cover is an appropriate cover for the particular static guide vane. 
     
     
         15 . A gas turbine engine comprising:
 a fan section and a compressor section, with said fan section including a fan rotor; and   a row of static guide vanes, the static guide vanes having an outer platform and an inner platform, said inner and outer platforms connected by an airfoil, said airfoil having channels extending into a main body of said airfoil to reduce the weight of said vane, and a cover closing off said channels with said cover providing a portion of said airfoil.   
     
     
         16 . The gas turbine engine as set forth in  claim 15 , wherein there are a plurality of said channels extending in a generally radial direction from said inner platform toward said outer platform, and spaced from a leading edge of said airfoil towards a trailing edge of said airfoil. 
     
     
         17 . The gas turbine engine as set forth in  claim 16 , wherein said channels extend for a greater width, with the width defined between the leading and trailing edges as the channels approach the trailing edge. 
     
     
         18 . The gas turbine engine as set forth in  claim 16 , wherein there are ribs intermediate said plurality of channels. 
     
     
         19 . The gas turbine engine as set forth in  claim 18 , wherein said ribs, and portions of a recess between said channels and said trailing and leading edges together form a planar surface for supporting said cover. 
     
     
         20 . The gas turbine engine as set forth in  claim 15 , wherein there are a plurality of said channels extending in a generally radial direction from said inner platform toward said outer platform, and spaced from a leading edge of said airfoil towards a trailing edge of said airfoil, said channels extend for a greater width, with the width defined between the leading and trailing edges, as the channels approach the trailing edge, there are ribs intermediate said plurality of channels, and portions of a recess between said channels and said trailing and leading edges together form a planar surface for supporting said cover.